[Federal Register Volume 63, Number 38 (Thursday, February 26, 1998)]
[Rules and Regulations]
[Pages 9734-9736]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-3795]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-131-AD; Amendment 39-10342; AD 98-04-30]
RIN 2120-AA64
Airworthiness Directives; Glaser-Dirks Flugzeugbau GmbH Model DG-
500M Gliders
AGENCY: Federal Aviation Administration, DOT.
ACTION: Direct final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to all Glaser-Dirks Flugzeugbau GmbH (DG Flugzeugbau) Model DG-
500M gliders. This AD requires repetitively inspecting the propeller
mounting plate for cracks, replacing any cracked propeller mounting
plate, and modifying the bolt connections of the propeller mounting
plate. This AD is the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for Germany.
The actions specified in this AD are intended to prevent the propeller
mounting plate from separating from the glider, which could result in
propeller separation and possible loss of control of the glider.
DATES: Effective May 15, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 15, 1998.
Comments for inclusion in the Rules Docket must be received on or
before March 19, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 97-CE-131-AD, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106.
Service information that applies to this AD may be obtained from DG
Flugzeugbau GmbH, P.O. Box 4120, 76625 Bruchsal, Germany; telephone:
+49 7257-89-0; facsimile: +49 7257-8922. This information may also be
examined at the Federal Aviation Administration (FAA), Central Region,
Office of the Regional Counsel, Attention: Rules Docket No. 97-CE-131-
AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mr. Mike Kiesov, Aerospace Engineer,
Small Airplane Directorate, Aircraft Certification Service, FAA, 1201
Walnut, suite 900, Kansas City, Missouri 64106; telephone: (816) 426-
6934; facsimile: (816) 426-2169.
SUPPLEMENTARY INFORMATION:
Events Leading to the Issuance of This AD
The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority
for Germany, recently notified the FAA that an unsafe condition may
exist on all DG Flugzeugbau Model DG-500M airplanes. The LBA reports
that, during an inspection, cracks were found on the lower end of the
propeller mounting plate near the bolt connections on one of the
affected gliders.
This condition, if not corrected in a timely manner, could result
in separation of the propeller mounting plate from the glider, which
could result in propeller separation and possible loss of control of
the glider.
Relevant Service Information
DG Flugzeugbau has issued Technical Note TN 843/8, dated April 10,
1997, which specifies procedures for inspecting the propeller mounting
plate for cracks, replacing any cracked propeller mounting plate, and
modifying the bolt connections of the propeller mounting plate.
The LBA classified this technical note as mandatory and issued
German AD 97-224, dated July 31, 1997, in order to assure the continued
airworthiness of these airplanes in Germany.
The FAA's Determination
This glider model is manufactured in Germany and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the LBA has kept the FAA informed of
the situation described above.
The FAA has examined the findings of the LBA; reviewed all
available information, including the service information referenced
above; and determined that AD action is necessary for products of this
type design that are certificated for operation in the United States.
Explanation of the Provisions of This AD
Since an unsafe condition has been identified that is likely to
exist or develop in other DG Flugzeugbau Model DG-500M gliders of the
same type design registered in the United States, the FAA is issuing an
AD. This AD requires inspecting the propeller mounting plate for
cracks, replacing any cracked propeller mounting plate, and modifying
the bolt connections of the propeller mounting plate.
[[Page 9735]]
Accomplishment of the actions of this AD would be required in
accordance with the previously referenced technical note.
Cost Impact
The FAA estimates that 5 gliders in the U.S. registry will be
affected by this AD, that it will take approximately 5 workhours per
glider to accomplish the initial inspection required by this AD, and
that the average labor rate is approximately $60 per work hour. Parts
cost approximately $120 per glider. Based on these figures, the cost
impact of this AD on U.S. operators is estimated to be $2,100, or $420
per airplane. These figures are only based on the cost of the initial
inspection and do not take into account the cost of repetitive
inspections. The FAA has no way of determining the number of repetitive
inspections each owner/operator of the affected gliders will incur.
The Direct Final Rule Procedure
The FAA anticipates that this regulation will not result in adverse
or negative comment and therefore is issuing it as a direct final rule.
The requirements of this direct final rule address an unsafe condition
identified by a foreign civil airworthiness authority and do not impose
a significant burden on affected operators. In accordance with section
11.17 of the Federal Aviation Regulations (14 CFR 11.17), unless a
written adverse or negative comment, or a written notice of intent to
submit an adverse or negative comment, is received within the comment
period, the regulation will become effective on the date specified
above. After the close of the comment period, the FAA will publish a
document in the Federal Register indicating that no adverse or negative
comments were received and confirming the date on which the final rule
will become effective. If the FAA does receive, within the comment
period, a written adverse or negative comment, or written notice of
intent to submit such a comment, a document withdrawing the direct
final rule will be published in the Federal Register, and a notice of
proposed rulemaking may be published with a new comment period.
Comments Invited
Although this action is in the form of a final rule and was not
preceded by notice and an opportunity for public comment, comments are
invited on this rule. Interested persons are invited to comment on this
rule by submitting such written data, views, or arguments as they may
desire. Communications shall identify the Rules Docket number and be
submitted in triplicate to the address specified under the caption
ADDRESSES. All communications received on or before the closing date
for comments will be considered, and this rule may be amended in light
of the comments received. Factual information that supports the
commenter's ideas and suggestions is extremely helpful in evaluating
the effectiveness of the AD action and determining whether additional
rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 97-CE-131-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is noncontroversial and
unlikely to result in adverse or negative comments. For reasons
discussed in the preamble, I certify that this regulation (1) Is not a
``significant regulatory action'' under Executive Order 12866; (2) is
not a ``significant rule'' under DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and (3) will not have a significant
economic impact, positive or negative, on a substantial number of small
entities under the criteria of the Regulatory Flexibility Act. A final
evaluation has been prepared for this action and is contained in the
Rules Docket. A copy of it may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
98-04-30 Glaser-Dirks Flugzeugbau GmbH: Amendment 39-10342; Docket
No. 97-CE-131-AD.
Applicability: Model DG-500M gliders, all serial numbers,
certificated in any category.
Note 1: This AD applies to each glider identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For gliders that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (e) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated in the body of this AD, unless
already accomplished.
To prevent the propeller mounting plate from separating from the
glider, which could result in propeller separation and possible loss
of control of the glider, accomplish the following:
(a) Within the next 5 hours time-in-service (TIS) after the
effective date of this AD, and thereafter at intervals not to exceed
25 hours TIS, inspect the propeller mounting plate for cracks in
accordance with the Instructions section of DG Flugzeugbau Technical
Note TN 843/8, dated April 10, 1997.
(b) If any cracked propeller mounting plate is found during any
inspection required by paragraph (a) of this AD, prior to further
flight, replace any cracked propeller mounting plate with a new
propeller mounting plate or FAA-approved propeller mounting plate in
accordance with the above-referenced technical note.
(c) Within the next 5 hours TIS after the effective date of this
AD, modify the bolt connections of the propeller mounting plate by
inserting an aluminum plate between the
[[Page 9736]]
propeller mounting plate and the washers of the bolt connections.
Accomplish this modification in accordance with DG Flugzeugbau
Technical Note TN 843/8, dated April 10, 1997.
(d) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the glider to a location where the
requirements of this AD can be accomplished.
(e) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
used if approved by the Manager, Small Airplane Directorate, FAA,
1201 Walnut, suite 900, Kansas City, Missouri 64106. The request
shall be forwarded through an appropriate FAA Maintenance Inspector,
who may add comments and then send it to the Manager, Small Airplane
Directorate.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Small Airplane Directorate.
(f) Questions or technical information related to DG Flugzeugbau
Technical Note TN 843/8 dated April 10, 1997, should be directed to
DG Flugzeugbau GmbH, P.O. Box 4120, 76625 Bruchsal, Germany;
telephone: +49 7257-89-0; facsimile: +49 7257-8922. This service
information may be examined at the FAA, Central Region, Office of
the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City.
(g) The inspections and replacements required by this AD shall
be done in accordance with DG Flugzeugbau Technical Note TN 843/8
dated April 10, 1997. This incorporation by reference was approved
by the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Copies may be obtained from DG Flugzeugbau
GmbH, P.O. Box 4120, 76625 Bruchsal, Germany. Copies may be
inspected at the FAA, Central Region, Office of the Regional
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at
the Office of the Federal Register, 800 North Capitol Street, NW,
suite 700, Washington, DC.
Note 3: The subject of this AD is addressed in German AD 97-224,
dated July 31, 1997.
(h) This amendment (39-10342) becomes effective on May 15, 1998.
Issued in Kansas City, Missouri, on February 6, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-3795 Filed 2-25-98; 8:45 am]
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